Thrust reverser for a turbofan gas turbine engine

The invention relates to thrust reversers for turbofan gas turbine engines.

Thrust reversers on gas turbine engines have to fulfill two functions: while stowed, to provide an exhaust nozzle for the direct thrust generated by the engine; and while deployed, to redirect the engine thrust to order to provide a decelerating force after landing. Since almost the entire flight sequence occurs with the thrust reverser in the stowed position, it is desirable that the presence of the thrust reverser does not degrade the direct thrust performance of the engine.

While many thrust reversers models have been used successfully for a number of years, there is a need to provide an improved arrangement.

In one aspect, the present concept provides a thrust reverser for a turbofan engine, the thrust reverser comprising at least first and second doors pivotally connected to a jet pipe, the jet pipe having an exit defined by an exit profile, each door having an outer skin and an inner skin mounted to the outer skin, the inner skin extending along only a portion of an axial length of the outer skin, the inner skin of the doors having edges that matingly engage the edges of the jet pipe substantially along the length of the exit profile.

In another aspect, the present concept provides a thrust reverser comprising: a jet pipe having an inner flow surface for receiving engine exhaust gases, the jet pipe having a circular portion and two arms extending rearward of the circular portion; and a pair of opposed doors pivotally connected to the jet pipe arms, each door having an inner flow surface in registry with the inner flow surface of the jet pipe and mating therewith to engage the jet pipe along its exit length when the doors are closed, wherein the inner surface of the jet pipe and the inner surfaces of the doors co-operate to provide a nozzle for engine exhaust gases.

In another aspect, the present concept provides a thrust reverser for a turbofan engine, the thrust reverser comprising an interior wall defining a continuous nozzle interior surface from a nozzle inlet to a thrust reverser exit when the doors are in a stowed position, the nozzle interior surface co-operatively defined by an internal surface of a jet pipe of the thrust reverser, internal surfaces of a plurality of closed thrust reverser doors of the thrust reverser, and seals extending between the jet pipe and each door substantially along an interface between the jet pipe and said door.

Further details of these and other aspects of the improvements presented herein will be apparent from the detailed description and appended figures.

BRIEF DESCRIPTION OF THE FIGURES

FIG. 1 is a side view of an example of a nacelle provided with a thrust reverser according to the present arrangement, its doors being shown in a stowed position;

FIG. 2 is a schematic side view of the thrust reverser of FIG. 1, with doors shown in a deployed position;

FIG. 3 is a rear view of what is shown in FIG. 2;

FIG. 4 is a schematic longitudinal cross-sectional view showing an example of the improved arrangement with the thrust reverser doors in the stowed position;

FIG. 5 is a view similar to FIG. 4, showing the doors in a deployed position;

FIG. 6 is an isometric view showing an example of an improved upper door;

FIG. 7 is an isometric view showing an example of an improved lower door;

FIG. 8 is a cross-section through lines 8-8 of FIG. 1;

FIG. 9A is an isometric view of the upper seal shown in FIG. 4 and FIG. 9B is an enlarged cross section of an example of the seal mounted to the jet pipe; and

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Industry Class:
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